US8892408B2ActiveUtilityPatentIndex 55
Generating inviscid and viscous fluid flow simulations over a surface using a quasi-simultaneous technique
Est. expiryMar 23, 2031(~4.7 yrs left)· nominal 20-yr term from priority
G06F 2111/10G06F 30/23G06F 17/5018G06F 2217/16
55
PatentIndex Score
3
Cited by
102
References
24
Claims
Abstract
A fluid-flow simulation over a computer-generated surface is generated using a quasi-simultaneous technique. The simulation includes a fluid-flow mesh of inviscid and boundary-layer fluid cells. An initial fluid property for an inviscid fluid cell is determined using an inviscid fluid simulation that does not simulate fluid viscous effects. An initial boundary-layer fluid property a boundary-layer fluid cell is determined using the initial fluid property and a viscous fluid simulation that simulates fluid viscous effects. An updated boundary-layer fluid property is determined for the boundary-layer fluid cell using the initial fluid property, initial boundary-layer fluid property, and an interaction law. The interaction law approximates the inviscid fluid simulation using a matrix of aerodynamic influence coefficients computed using a two-dimensional surface panel technique and a fluid-property vector. An updated fluid property is determined for the inviscid fluid cell using the updated boundary-layer fluid property.
Claims
exact text as granted — not AI-modifiedWe claim:
1. A computer-implemented method of generating a fluid-flow simulation over a computer-generated surface using one or more processors, the simulation including an inviscid fluid-flow mesh comprised of a plurality of inviscid fluid cells and a viscous fluid-flow mesh comprised of a plurality of boundary-layer fluid cells, at least some of the boundary-layer fluid cells being on or adjacent to the computer-generated surface, the method comprising:
determining, using the one or more processors, an initial fluid property, for at least one inviscid fluid cell using an inviscid fluid simulation that does not simulate fluid viscous effects;
determining, using the one or more processors, an initial boundary-layer fluid property for at least one of the boundary-layer fluid cells using the initial fluid property and a viscous fluid simulation that simulates fluid viscous effects,
wherein the at least one inviscid fluid cell is located in relation to the at least one boundary-layer fluid cell such that an updated boundary-layer fluid property for the at least one boundary-layer fluid cell is influenced by the at least one inviscid fluid cell;
determining, using the one or more processors, the updated boundary-layer fluid property for the at least one boundary-layer fluid cell using the initial fluid property, initial boundary-layer fluid property, and an interaction law,
wherein the interaction law approximates the inviscid fluid simulation using a matrix of aerodynamic influence coefficients computed using a two-dimensional surface panel technique and a fluid-property vector;
determining, using the one or more processors, an updated fluid property for the at least one inviscid fluid cell using the updated boundary-layer fluid property.
2. The computer-implemented method of claim 1 , wherein the initial fluid property is an initial fluid velocity and the updated fluid property is an updated fluid velocity.
3. The computer-implemented method of claim 1 , wherein the initial boundary-layer fluid property is an initial displacement thickness and the updated boundary-layer fluid property is an updated displacement thickness.
4. The computer-implemented method of claim 1 , wherein the matrix of aerodynamic influence coefficients is adapted to account for compressibility by dividing each row by (1−M 1 2 ) 1/2 , wherein M 1 is the local Mach number.
5. The computer-implemented method of claim 1 , wherein a fluid property of the fluid property vector is determined using the following relation to simulate supersonic flow conditions:
u
e
(
n
+
1
)
=
u
e
(
n
)
-
1
M
ei
2
-
1
(
ⅆ
m
(
n
)
ⅆ
s
-
ⅆ
m
(
n
+
1
)
ⅆ
s
)
,
where u e(n+1) is the edge velocity at time step n+1, u e(n) is the edge velocity at time step n, M ei is the local Mach number, and m (n) and m (n+1) is the product of: edge density ρ e , edge velocity u e , and boundary-layer thickness δ* at time step n and time step n+1, respectively.
6. The computer-implemented method of claim 1 , wherein a fluid property of the fluid property vector is determined using the following relation to simulate supersonic flow conditions over a swept/tapered wing:
u
e
(
n
+
1
)
=
u
e
(
n
)
-
1
M
ei
2
-
1
(
v
w
(
n
+
1
)
-
v
w
(
n
)
)
,
where u e(n+l) is the edge velocity at time step n+1, u e(n) is the edge velocity at time step n, M ei is the local Mach number, and v w(n+1) and v w(n) are the transpiration velocities at the surface at time step n and time step n+1, respectively.
7. The computer-implemented method of claim 1 , wherein the matrix of aerodynamic influence coefficients is adapted row-by-row to implement either the subsonic or supersonic interaction law depending on the local Mach number.
8. The computer-implemented method of claim 7 , wherein the matrix of aerodynamic influence coefficients is further adapted to utilize a linear weighted average of the subsonic and supersonic interaction laws to approximate the changes to the inviscid fluid flow for local Mach numbers near Mach 1.
9. The computer-implemented method of claim 8 , wherein the linear weighted average is used for local Mach numbers ranging between about 0.97 and about 1.03.
10. The computer-implemented method of claim 1 , wherein the matrix of aerodynamic influence coefficients is adapted using a curvature correction to approximate a boundary layer characterized as having a thickness and a curvature.
11. The computer-implemented method of claim 1 , wherein the interaction law approximates the inviscid fluid simulation using a matrix of aerodynamic influence coefficients computed using an axisymmetric surface panel technique instead of a two-dimensional surface panel technique.
12. The computer-implemented method of claim 1 , wherein the computer-generated surface is a computer-generated wing surface of an aircraft.
13. A non-transitory computer-readable storage medium comprising computer-executable instructions for generating a fluid-flow simulation over a computer-generated surface, the simulation including an inviscid fluid-flow mesh comprised of a plurality of inviscid fluid cells and a viscous fluid-flow mesh comprised of a plurality of boundary-layer fluid cells, at least some of the boundary-layer fluid cells being on or adjacent to the computer-generated surface, the instructions for:
determining an initial fluid property, for at least one inviscid fluid cell using an inviscid fluid simulation that does not simulate fluid viscous effects;
determining an initial boundary-layer fluid property for at least one of the boundary-layer fluid cells using the initial fluid property and a viscous fluid simulation that simulates fluid viscous effects,
wherein the at least one inviscid fluid cell is located in relation to the at least one boundary-layer fluid cell such that an updated boundary-layer fluid property for the at least one boundary-layer fluid cell is influenced by the at least one inviscid fluid cell;
determining the updated boundary-layer fluid property for the at least one boundary-layer fluid cell using the initial fluid property, initial boundary-layer fluid property, and an interaction law,
wherein the interaction law approximates the inviscid fluid simulation using a matrix of aerodynamic influence coefficients computed using a two-dimensional surface panel technique and a fluid-property vector;
determining an updated fluid property for the at least one inviscid fluid cell using the updated boundary-layer fluid property.
14. The computer-readable medium of claim 13 , wherein the initial fluid property is an initial fluid velocity and the updated fluid property is an updated fluid velocity.
15. The computer-readable medium of claim 13 , wherein the initial boundary-layer fluid property is an initial displacement thickness and the updated boundary-layer fluid property is an updated displacement thickness.
16. The computer-readable medium of claim 13 , wherein the matrix of aerodynamic influence coefficients is adapted to account for compressibility by dividing each row by (1−M 1 2 ) 1/2 , wherein M 1 is the local Mach number.
17. The computer-readable medium of claim 13 , wherein a fluid property of the fluid property vector is determined using the following relation to simulate supersonic flow conditions:
u
e
(
n
+
1
)
=
u
e
(
n
)
-
1
M
ei
2
-
1
(
ⅆ
m
(
n
)
ⅆ
s
-
ⅆ
m
(
n
+
1
)
ⅆ
s
)
,
where u e(n+1) is the edge velocity at time step n+1, u e(n) is the edge velocity at time step n, M ei is the local Mach number, and m (n) and m( n+1) is the product of: edge density ρ e , edge velocity u e , and boundary-layer thickness δ* at time step n and time step n+1, respectively.
18. The computer-readable medium of claim 13 , wherein a fluid property of the fluid property vector is determined using the following relation to simulate supersonic flow conditions over a swept/tapered wing:
u
e
(
n
+
1
)
=
u
e
(
n
)
-
1
M
ei
2
-
1
(
v
w
(
n
+
1
)
-
v
w
(
n
)
)
,
where u e(n+1) is the edge velocity at time step n+1, u e(n) is the edge velocity at time step n, M ei is the local Mach number, and v w(n+1) and v w(n) are the transpiration velocities at the surface at time step n and time step n+1, respectively.
19. The computer-readable medium of claim 13 , wherein the matrix of aerodynamic influence coefficients is adapted row-by-row to implement either the subsonic or supersonic interaction law depending on the local Mach number.
20. The computer-readable medium of claim 19 , wherein the matrix of aerodynamic influence coefficients is further adapted to utilize a linear weighted average of the subsonic and supersonic interaction laws to approximate the changes to the inviscid fluid flow for local Mach numbers near Mach 1.
21. The computer-readable medium of claim 20 , wherein the linear weighted average is used for local Mach numbers ranging between about 0.97 and about 1.03.
22. The computer-readable medium of claim 13 , wherein the matrix of aerodynamic influence coefficients is adapted using a curvature correction to approximate a boundary layer characterized as having a thickness and a curvature.
23. The computer-readable medium of claim 13 , wherein the interaction law approximates the inviscid fluid simulation using a matrix of aerodynamic influence coefficients computed using an axisymmetric surface panel technique instead of a two-dimensional surface panel technique.
24. The computer-readable medium of claim 13 , wherein the computer-generated surface is a computer-generated wing surface of an aircraft.Cited by (0)
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